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display “Check Fuel Flow” in a red advisory box in the lower right
corner of the MFD.
28 VDC for the digital instrument operation is supplied through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
Fuel Caution Light
The amber FUEL caution light in the annunciator panel comes on to
indicate a low fuel condition. The light is illuminated by switches in the
fuel quantity indicator if the fuel quantity in both tanks drops below
approximately 14 gallons (28 gallons total with tanks balanced in level
flight). Since both tanks must be below 14 gallons to illuminate the
light, the light could illuminate with as little as 14 gallons in one tank
during level flight if the other tank is allowed to run dry. If the FUEL
caution light comes on in flight, refer to the Fuel Quantity gages to
determine fuel quantity. The light is powered by 28 VDC through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
Revision A5
P/N 13772-001 7-61
Cirrus Design Section 7
SR22 Airplane Description
Boost Pump Switch
Boost pump operation and engine prime is controlled through the Fuel
Pump BOOST-PRIME switch located adjacent to the fuel selector
valve. The PRIME position is momentary and the BOOST position is
selectable. A two-speed prime allows the fuel pressure to rapidly
achieve proper starting pressure.
Serials 0002 through 0277 before SB 22-73-01: For engine starting,
pressing PRIME causes the boost pump to operate at high speed until
the fuel pressure reaches 2-4 psi. When the fuel pressure reaches the
2-4 psi range, a pressure switch in the fuel injection line switches the
boost pump to the low-speed mode to provide a 4-6 psi fuel pressure
boost. Selecting BOOST energizes the boost pump in low-speed
mode to deliver a continuous 4-6 psi boost to the fuel flow for vapor
suppression in a hot fuel condition.
Serials 0278 and subs, and serials 0002 through 0277 after SB 22-73-
01: An oil pressure based system is used to control boost pump
operation. The oil pressure/oil temperature sensor provides a signal to
the starting circuit/DAU to generate a ground for the oil annunciator
and the fuel system. This system allows the fuel pump to run at high
speed (PRIME) when the engine oil pressure is less than 10 PSI.
Whenever the engine oil pressure exceeds 10 PSI, pressing PRIME
will have no effect. Selecting BOOST energizes the boost pump in lowspeed
mode regardless of oil pressure to deliver a continuous 4-6 psi
boost to the fuel flow for vapor suppression in a hot fuel condition.
The boost pump operates on 28 VDC supplied through the 5-amp
FUEL PUMP circuit breaker on Main Bus 2.
Revision A5
7-62 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Brake System
The main wheels have hydraulically operated, single-disc type brakes,
individually activated by floor mounted toe pedals at both pilot stations.
A parking brake mechanism holds induced hydraulic pressure on the
disc brakes for parking.
The brake system consists of a master cylinder for each rudder pedal,
a hydraulic fluid reservoir, a parking brake valve, a single disc brake
assembly on each main landing gear wheel, and associated hydraulic
plumbing. Braking pressure is initiated by depressing the top half of a
rudder pedal (toe brake). The brakes are plumbed so that depressing
either the pilot’s or copilot’s left or right toe brake will apply the
respective (left or right) main wheel brake. The reservoir is serviced
with Mil-H-5606 hydraulic fluid.
Brake system malfunction or impending brake failure may be indicated
by a gradual decrease in braking action after brake application, noisy
or dragging brakes, soft or spongy pedals, excessive travel, and/or
weak braking action. Should any of these symptoms occur, immediate
maintenance is required. If, during taxi or landing roll, braking action
decreases, let up on the toe brakes and then reapply the brakes with
heavy pressure. If the brakes are spongy or pedal travel increases,
pumping the pedals may build braking pressure.
Refer to Section 10, Safety Information, for Brake System operational
considerations.
Revision A6
P/N 13772-001 7-63
Cirrus Design Section 7
SR22 Airplane Description
Parking Brake
• Caution •
Do not pull the PARK BRAKE knob in flight. If a landing is
made with the parking brake valve set, the brakes will maintain
any pressure applied after touchdown.
The main wheel brakes are set for parking by using the PARK BRAKE
knob on the left side of the console near the pilot’s right ankle. Brake
　
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